(3)  
Close all flight control circuit breakers on P6 circuit breaker panel.

(4)  
Pressurize hydraulic reservoirs as required. Refer to 29-09-300.

500 
27-61-0 Page 204  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/73 

SPOILER CONTROL SYSTEM - ADJUSTMENT/TEST
1. General
A.  The spoiler control system provides lateral control and speed brake signals through the spoiler mixer to the flight spoiler actuators. The speed brake signals also control the ground spoilers. (See Speed Brake Control System, 27-62-0.)
WARNING:  ALL FLIGHT CONTROL SYSTEMS ARE FULLY POWERED. CHECK TO ENSURE THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL CONTROL SURFACES BEFORE TURNING HYDRAULIC POWER ON.
B.  Some airplanes have a metal-cal on the aileron control wheels, which is calibrated in degrees of control wheel rotation. These metal-cals are for flight crew use. Do not use these metal-cals when adjusting or testing the spoiler control system.
C.  The following conditions must be met before adjusting or testing the spoiler control system:
(1)  
Aileron control system must be properly adjusted. Refer to 27-11-0, Aileron and Aileron Trim Control System - Adjustment/Test.

(2)  
Wing trailing edge flaps must be properly adjusted. Refer to 27-51-0, Trailing Edge Flap System - Adjustment/Test.

(3)  
Speed brake system must be properly adjusted. However, both systems must be in adjustment/prior to testing either system. Refer to 27-62-0, Speed Brake Control System -Adjustment/Test.

2.  Spoiler Control System Adjustment
A.  General
(1)  The spoiler control system will be properly adjusted when the individual components are adjusted to meet the following conditions. See figure 501 for rigging pin locations and cable tension requirements.
(a)  Right Aileron Control Cables
1)  With rigging pins A/S-1 and A/S-14 installed, rigging pin A/S-3 fits freely and cable tension is within 15 pounds of required value. If not, these conditions may be met by adjusting turnbuckles in lower nose compartment per paragraph C.(2).
500 
Aug 15/69  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-61-0 Page 501 

G29432G54254
Spoiler Control System - Rigging Pin Locations and Cable Tension  500 
27-61-0  Figure 501  May 15/81 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500 Spoiler Control System - Rigging Pin Locations and Cable Tension Aug 15/68 Figure 501 (Sheet 2) Page 502A/502B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(b)  
Aileron Spring Cartridge

1)  With rigging pins A/S-3 and A/S-4 installed, the aileron spring cartridge is not deflected. This condition may be checked by removing rod end bolt and checking that it may be reinstalled freely. If not, this condition may be met by adjusting rod end per par. C.(3).

(c)  
Adjust Spoiler Wing Cables

1)  With rigging pin A/S-14 installed rigging pins A/S-8, A/S-9, A/S-10, and A/S-11 fit freely and cable tension is within 15 pounds of required value. If not, these conditions may be met by adjusting turnbuckles in wheel well per par. C.(4).

(d)  
Ratio Changer Input Rod

1)  With rigging pin A/S-14 installed, rigging pin A/S-3 fits freely. If not, this condition may be met by adjusting ratio changer input rod per par. C.(5).

(e)  
Spoiler to Flap Clearance (Hydraulic Power On)

1)  With hydraulic power on, retract the flaps to the up position by placing the flap control lever in the FLAP UP detent. The flight spoiler to flap clearance is 0.03 + 0.10/-0.00 inch measured at actuator centerline. If not, this condition may be met by adjusting actuator rod end per par. C.(6).
(f) Spoiler Actuator Input Lever (Hydraulic Power On) 1) When rotating the captain's control wheel from 50 degrees counterclockwise toward neutral the No. 2 and 3 flight spoilers reach full down at the 4 + 2 degree counterclockwise wheel position. 2) When rotating the captain's control wheel from 50 degrees clockwise toward neutral the No. 6 and 7 flight spoilers reach full down at the 4 + 2 degree clockwise wheel position.
3)  Requirements 1) or 2) may be met by adjusting actuator input lever per par. C.(7).
500 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-61-0 Page 503 

(g)  Spoiler Mix (Hydraulic Power On) (Optional)
NOTE:  This check is optional, and need be performed only if spoiler full up and down travel responses at zero speed brakes per par. 3.D.(1) are not met.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(89)